EP1946224A2 - Automatische doppelte rotorendrehzahlsteuerung für helikopter - Google Patents

Automatische doppelte rotorendrehzahlsteuerung für helikopter

Info

Publication number
EP1946224A2
EP1946224A2 EP06851713A EP06851713A EP1946224A2 EP 1946224 A2 EP1946224 A2 EP 1946224A2 EP 06851713 A EP06851713 A EP 06851713A EP 06851713 A EP06851713 A EP 06851713A EP 1946224 A2 EP1946224 A2 EP 1946224A2
Authority
EP
European Patent Office
Prior art keywords
speed
predetermined
control system
flight control
altitude
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06851713A
Other languages
English (en)
French (fr)
Other versions
EP1946224B1 (de
EP1946224A4 (de
Inventor
Greg W. Barnes
Eileen F. Horbury
Eric W. Jacobs
Kenneth J. Buckman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sikorsky Aircraft Corp
Original Assignee
Sikorsky Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sikorsky Aircraft Corp filed Critical Sikorsky Aircraft Corp
Publication of EP1946224A2 publication Critical patent/EP1946224A2/de
Publication of EP1946224A4 publication Critical patent/EP1946224A4/de
Application granted granted Critical
Publication of EP1946224B1 publication Critical patent/EP1946224B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B64C27/57—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust

Definitions

  • the present invention is directed to helicopter rotor speed controls. More specifically, the present invention is directed to automatic dual rotor speed controls, which automatically transition between a high rotor speed and a lower rotor speed based upon received flight information.
  • Many helicopters include a main rotor and a tail rotor that are integrally connected together and driven by one or more engines.
  • One known method for reducing a helicopter's noise level is to reduce the speed of the main and tail rotors. That is, it is known in the art to design a helicopter with a system, which incorporates a variable speed that enables the pilot to manually vary the speed of the main and tail rotors from a normal mode (e.g., high rotor speed) to a quiet mode (e.g., low rotor speed).
  • a flight control system for a helicopter having a main rotor and a tail rotor includes an automatic rotor speed control being configured to transition the main rotor and the tail rotor between a high speed and a low speed based upon a plurality of received information without requiring any pilot action, the plurality of received information comprising height above ground level, knot indicated air speed, outside air temperature, barometric altitude, pressure altitude, density altitude, and an engine operational status.
  • the automatic rotor speed control transitions the main and tail rotors from the low speed to the high speed if the plurality of received information comprises any one of a plurality of inhibits. In other embodiments, the automatic rotor speed control transitions the main and tail rotors from the high speed to the low speed if the plurality of received information comprises one or more acceptance conditions.
  • a flight control system for a helicopter having a main rotor and a tail rotor is also provided.
  • the flight control system includes a full authority digital engine controller for each engine of the helicopter, an air data computers for collecting and determining a plurality of flight data, a radar altimeters for collecting height above ground level data, and an automatic rotor speed control resident on the full authority digital engine controller.
  • the automatic rotor speed control is configured to control the full authority digital engine controller to automatically adjust the speed of rotors of the helicopter based upon the plurality of flight data and the height above ground level data.
  • a helicopter having a main rotor, a tail rotor, a flight control system, and an automatic rotor speed control resident on the flight control system is provided.
  • the automatic rotor speed control is configured to transition a speed of the main and tail rotors between a high speed and a low speed based on received flight information without requiring any pilot action.
  • FIG. 1 is schematic diagram of a flight control system having an automatic rotor speed control according to the present disclosure
  • FIGS. 2 and 3 are flow charts illustrating the automatic rotor speed control of FIG. 1 ;
  • FIG. 4 is a graph illustrating outside air temperature and altitude as a function of the automatic rotor speed control of the present disclosure.
  • FIG. 5 is a graph illustrating air speed and rotor speed as a function of the automatic rotor speed control of the present disclosure.
  • flight control system 10 is generally referred to by reference number 10 and is shown configured for use with a helicopter (not shown) having two engines.
  • flight control system 10 includes automatic rotor speed control 12 resident thereon.
  • Rotor speed control 12 is configured to automatically transition the helicopter's main and tail rotors from a high-speed to a low-speed based on one or more types of received flight information. In this manner, flight control system 10 having rotor speed control 12 can switch to and from a low noise operational mode without requiring any pilot action.
  • Flight control system 10 includes a Full Authority Digital Engine Controller (FADEC) 14 for each engine.
  • flight control system 10 includes a primary FADEC 14a and a secondary FADEAC 14b for each engine.
  • Control 12 is resident on each FADEC 14.
  • FADEC Full Authority Digital Engine Controller
  • flight control system 10 functions in a manner known in the art by collecting various flight data and communicating this flight data to the pilot(s).
  • flight control system 10 For collecting flight data and information, flight control system 10 includes one or more air data computers 16 (three shown) for collecting and determining a plurality of flight data including, but not limited to, knot indicated air speed (KIAS), outside air temperature (OAT), barometric altitude (BA), pressure altitude (PA), density altitude (DA), and other data. Flight control system 10 also includes one or more radar altimeters 18 (two shown) for collecting flight data such as a height above ground level (AGL). Additionally, flight control system 10 includes one or more blade speed sensors 20 and one ore more collective position sensors 22.
  • air data computers 16 three shown for collecting and determining a plurality of flight data including, but not limited to, knot indicated air speed (KIAS), outside air temperature (OAT), barometric altitude (BA), pressure altitude (PA), density altitude (DA), and other data.
  • Flight control system 10 also includes one or more radar altimeters 18 (two shown) for collecting flight data such as a height above ground level (AGL). Additionally, flight control system 10 includes one or
  • flight control system 10 can include an active vibration controller 24 as is known in the art for controlling vibration induced from the blades.
  • Flight control system 10 further includes one or more vehicle monitoring modules 26 (two shown) that provide an interface between the various avionics systems and the FADEC 14.
  • vehicle monitoring modules 26 can receive information related to engine operational status, whether a training mode or a non-training is selected, and others.
  • flight control system 10 can include one or more flight control modules 28 (two shown) that can be used for automatic pilot operations.
  • flight control system 10 includes one or more pilot flight displays 30 (two shown), one or more multi-function displays 32 (two shown), and at least one integrated electronic stand-by instruments (IESI) 34.
  • pilot flight displays 30 two shown
  • multi-function displays 32 two shown
  • IESI integrated electronic stand-by instruments
  • Flight control system 10 communicates information among its components across one or more information buses 36.
  • flight control system 10 uses FADEC 14, pilot inputs, and the various received flight data to control the operation of the helicopter in a known manner.
  • flight control system 10 includes automatic rotor speed control 12 resident on FADEC 14, where the speed control is configured to control the FADEC to automatically adjust the rotor speed based upon one or more received flight data.
  • control 12 resident on FADEC 14 utilizes flight data such as, but not limited to KIAS, OAT, PA, DA and other information received from the helicopter's ADCs 16 and height AGL received from the helicopter's radar altimeters 18.
  • Control 12 utilizes this information to determine when to automatically transition the helicopter's main and tail rotor speeds back-and- forth between a high speed (e.g., approximately 107%) and a low speed (e.g., approximately 102%).
  • the use of the ADCs 16 and radar altimeters 18 to obtain the desired parameters can be accomplished by any means known in the art.
  • the varying of the main and tail rotor speeds can be accomplished by any method known in the art.
  • control 12 transitions the main and tail rotors from a low speed (e.g., speed of 102%) to a high speed (e.g., speed of 107%) if any one of a plurality of inhibits 38 is detected.
  • the inhibits 38 can include (1) only one engine is operative, (2) a height above ground level is below a predetermined height (e.g., 150 feet), (3) a pressure altitude is at or above a predetermined altitude (e.g., 3500 feet), (4) a density altitude is at or above a predetermined altitude (e.g., 4000 feet), (5) an outside air temperature is at or above a predetermined temperature (e.g., 40 degrees Celsius), (6) a knot indicated air speed is below a predetermined speed (e.g., 50 knots), and (7) a training mode is selected.
  • a predetermined height e.g. 150 feet
  • a pressure altitude is at or above a predetermined altitude (e.g., 3500 feet)
  • a density altitude is at or above a predetermined altitude (e.g., 4000 feet)
  • an outside air temperature is at or above a predetermined temperature (e.g., 40 degrees Celsius)
  • (6) a knot indicated air speed is
  • control 12 can, upon detection of inhibit 38, transition from the low speed to the high speed at a predetermined acceleration rate such as about 1% per second.
  • control 12 can, in some embodiments, require the inhibit 38 to be present for a predetermined period of time (e.g., three seconds) before transitioning the main and tail rotors from the low speed to the high speed.
  • a predetermined period of time e.g., three seconds
  • control 12 can, in some embodiments, provide stability to the helicopter by preventing transition back to the low speed until inhibit 38 has returned to at least a second inhibit 40. For example, if control 12 determines that the density altitude is at or above the predetermined altitude (e.g., 4000 feet) such that the control transitions from the low speed to the high speed, then the control can also inhibit transition back to the low speed until the density altitude is below a second predetermined altitude (e.g., 3800 feet). In this manner, control 12 can provide an envelop of operation where transitioning between high-and-low speeds and be inhibited to ensure operational stability to the helicopter.
  • the predetermined altitude e.g. 4000 feet
  • control 12 transitions the main and tail rotors from a high speed (e.g., speed of 107%) to a low speed (e.g., speed of 102%) if one or more acceptance conditions 42 is detected.
  • the acceptance conditions 42 can include (1) both engines being operative, (2) a height above ground level is at or above a predetermined height (e.g., 150 feet), (3) a pressure altitude is below a predetermined altitude (e.g., 3500 feet), (4) a density altitude is below a predetermined altitude (e.g., 4000 feet), (5) an outside air temperature is below a predetermined temperature (e.g., 40 degrees Celsius), (6) a knot indicated air speed is at or above a predetermined speed (e.g., 50 knots), (7) a non-training mode is selected, and any combinations thereof.
  • a predetermined height e.g. 150 feet
  • a pressure altitude is below a predetermined altitude (e.g., 3500 feet)
  • a density altitude is below a predetermined altitude (e.g., 4000 feet)
  • an outside air temperature is below a predetermined temperature (e.g., 40 degrees Celsius)
  • (6) a knot indicated air speed is at or above
  • control 12 can, upon detection of acceptance condition 42, transition from the high speed to the low speed at a predetermined deceleration rate such as about 1% per second.
  • control 12 can require the acceptance condition 42 to be present for a predetermined period of time (e.g., three seconds) before transitioning the main and tail rotors from the high speed to the low speed.
  • a predetermined period of time e.g., three seconds
  • FIG. 4 a Sikorsky S-76D helicopter having control 12 was analyzed.
  • a low rotor speed and high rotor speed are illustrated with respect to an outside air temperature and the DA altitude inhibit.
  • rotor speeds illustrate the envelope of operation between the DA altitude inhibit and the second predetermined altitude.
  • a Sikorsky S-76D helicopter having control 12 was analyzed.
  • a transition airspeed of 50 KIAS and a 150 ft AGL altitude inhibit were selected so as to not interfere with the Category A and B takeoff and landing profiles.
  • These methodologies could be applied to other helicopters resulting in slightly different transition airspeeds, outside air temperatures, altitude inhibits, and/or predetermined time periods with similar benefits.
  • flight control system 10 uses FADEC 14 having control 12 to automatically vary the main and tail rotor speeds depending upon received flight information.
  • control 12 significantly reduces the helicopter's external acoustic signature during takeoff, flyover, and descent profiles.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Feedback Control In General (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Toys (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)
EP06851713.5A 2005-10-03 2006-09-29 Automatische doppelte rotorendrehzahlsteuerung für helikopter Not-in-force EP1946224B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US72688305P 2005-10-03 2005-10-03
US11/536,128 US9235217B2 (en) 2005-10-03 2006-09-28 Automatic dual rotor speed control for helicopters
PCT/US2006/038453 WO2008048245A2 (en) 2005-10-03 2006-09-29 Automatic dual rotor speed control for helicopters

Publications (3)

Publication Number Publication Date
EP1946224A2 true EP1946224A2 (de) 2008-07-23
EP1946224A4 EP1946224A4 (de) 2013-06-05
EP1946224B1 EP1946224B1 (de) 2016-09-07

Family

ID=38054551

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06851713.5A Not-in-force EP1946224B1 (de) 2005-10-03 2006-09-29 Automatische doppelte rotorendrehzahlsteuerung für helikopter

Country Status (5)

Country Link
US (1) US9235217B2 (de)
EP (1) EP1946224B1 (de)
CN (1) CN101495368B (de)
CA (1) CA2627998A1 (de)
WO (1) WO2008048245A2 (de)

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ITTO20090079U1 (it) * 2009-06-10 2010-12-11 Agusta Spa Sistema per la gestione ed il controllo della velocita' di uno o piu' rotori di un aeromobile atto a volare a punto fisso
CN102591350A (zh) * 2011-01-06 2012-07-18 佛山市安尔康姆航拍科技有限公司 四旋翼无人飞行器的飞行控制方法和系统
DE102012003910A1 (de) 2011-04-15 2012-10-18 Ulrich Röhr System zur drahtlosen Steuerung eines RC-Modells, Sendeeinrichtung, Empfangseinrichtung sowie Verfahren
FR2987031B1 (fr) 2012-02-21 2014-10-24 Eurocopter France Aeronef a voilure muni d'un rotor arriere, et procede pour optimiser le fonctionnement d'un rotor arriere
US8682521B2 (en) * 2012-06-25 2014-03-25 The Boeing Company Unpredictable vehicle navigation
FR3000466B1 (fr) * 2012-12-27 2015-02-13 Eurocopter France Procede d'entrainement en rotation d'un rotor de giravion, par anticipation des besoins en couple entre deux consignes de vitesse de rotation du rotor
FR3000465B1 (fr) * 2012-12-27 2015-02-13 Eurocopter France Procede d'entrainement en rotation d'un rotor principal de giravion, selon une consigne de vitesse de rotation a valeur variable
US9174730B2 (en) 2013-08-21 2015-11-03 Sikorsky Aircraft Corporation Automated rotating tail rotor control
FR3023261B1 (fr) 2014-07-03 2016-07-01 Airbus Helicopters Methode de regulation de la vitesses de rotation du rotor principal d'un giravion multi-moteur en cas de panne de l'un des moteurs
WO2016054209A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Dual rotor, rotary wing aircraft
WO2016053408A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Acoustic signature variation of aircraft utilizing a clutch
FR3027124B1 (fr) 2014-10-14 2016-11-25 Airbus Helicopters Methode de regulation sous conditions givrantes de la vitesse d'entrainement d'un rotor de giravion
FR3028839B1 (fr) 2014-11-26 2016-11-18 Airbus Helicopters Methode d'assistance a la navigation d'un giravion multimoteur en cas de panne moteur, dans le cadre d'un entrainement a vitesse variable d'un rotor principal du giravion
FR3041606B1 (fr) 2015-09-25 2017-09-29 Airbus Helicopters Dispositif de regulation de la vitesse de rotation d'un rotor de giravion, giravion equipe d'un tel dispositif et methode de regulation associee
FR3061142B1 (fr) 2016-12-22 2019-01-25 Airbus Helicopters Dispositif de regulation de la vitesse de rotation d'un arbre d'un generateur de gaz de turbomoteur de giravion, giravion equipe d'un tel dispositif et methode de regulation associee
US10802482B2 (en) * 2017-02-27 2020-10-13 Textron Innovations Inc. Reverse tactile cue for rotorcraft rotor overspeed protection
FR3065756B1 (fr) 2017-04-28 2019-04-26 Airbus Helicopters Dispositif de regulation d'une consigne d'une vitesse de rotation d'un rotor de giravion, giravion equipe d'un tel dispositif et methode de regulation associee
US10703470B2 (en) * 2018-02-09 2020-07-07 Textron Innovations Inc. System and method for rotorcraft autorotation entry assist
US11072434B2 (en) * 2018-04-24 2021-07-27 Textron Innovations Inc. Method and system for controlling rotor speeds of rotor systems
FR3095638B1 (fr) 2019-04-30 2021-04-02 Airbus Helicopters Procédé de régulation d’une installation motrice d’un giravion et giravion associé
US11420735B2 (en) 2019-06-14 2022-08-23 Textron Innovations Inc. Multi-rotor noise control by automated distribution propulsion
US11420758B2 (en) 2019-06-14 2022-08-23 Textron Innovations Inc. Multi-rotor noise control by automated distribution propulsion
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Also Published As

Publication number Publication date
EP1946224B1 (de) 2016-09-07
CA2627998A1 (en) 2008-04-24
US20070118254A1 (en) 2007-05-24
CN101495368A (zh) 2009-07-29
US9235217B2 (en) 2016-01-12
EP1946224A4 (de) 2013-06-05
WO2008048245A2 (en) 2008-04-24
WO2008048245A3 (en) 2008-10-30
CN101495368B (zh) 2012-06-13

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